Assembly of turbine engine parts comprising a fan blade having an integrated platform, and corresponding turbine engine

a technology of integrated platform and turbine engine, which is applied in the direction of machines/engines, liquid fuel engines, mechanical equipment, etc., can solve the problems of reducing performance, complex parts of blades, and reducing aerodynamics, so as to reduce movement, improve aerodynamics, and limit the impact of drag

Active Publication Date: 2018-06-14
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0006]The object of the present invention is in particular to propose a solution that makes it possible to reduce the movements betwee

Problems solved by technology

The fan blade is a complex part, as its design requires a multi-disciplinary team which must cope at the same time with the aerodynamic, mechanical and acoustic aspects.
However, said blades may produce problems, for example manufacturing

Method used

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  • Assembly of turbine engine parts comprising a fan blade having an integrated platform, and corresponding turbine engine
  • Assembly of turbine engine parts comprising a fan blade having an integrated platform, and corresponding turbine engine
  • Assembly of turbine engine parts comprising a fan blade having an integrated platform, and corresponding turbine engine

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Embodiment Construction

[0029]FIG. 1 shows a turbine engine 50 such as a turbojet engine for an aircraft, to which the invention relates. Said turbine engine 50 is in this case a dual-flow turbine engine which extends along a longitudinal axis X. The turbine engine 50 generally comprises an external nacelle 51 that surrounds a gas generator 52, upstream of which a fan 30 is mounted. In the present invention, and in a general manner, the terms ‘upstream’ and ‘downstream’ are defined in relation to the circulation of gases in the turbine engine. The terms ‘upper’, ‘lower’, ‘outer’ and ‘inner’ are defined in relation to a radial axis Z perpendicular to the axis X and in relation to the distance relative to the longitudinal axis X. A transverse axis Y is also perpendicular to the longitudinal axis X and to the radial axis Z. Said axes, X, Y, Z, shown in FIG. 1, form an orthonormal coordinate system.

[0030]In this example, the gas generator 52 comprises, from upstream to downstream, a low-pressure compressor 54,...

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Abstract

The invention relates to an assembly of turbine engine (50) parts having a longitudinal axis (X), the assembly comprising at least two adjacent fan blades made of a 3D woven composite material, each blade (1) comprising a root (3), a vane (2) extending from the root (3), and an integrated platform (4) inserted between the root (3) and the vane (2), the platform (4) extending on either side of the vane (2) and forming a pressure face platform portion (4I) and a suction face platform portion (4E), the pressure face and suction face platform portions of adjacent blades being connected by a fin (14) extending at least radially at the outer side of the pressure face and suction face platform portions (4I, 4E), relative to the longitudinal axis (X), having a substantially triangular transverse cross section and extending axially and so as to upper overlap the longitudinal edges (11A, 11B) of the pressure face and suction face platform portions (4I, 4E) of the adjacent blades.

Description

1. FIELD OF THE INVENTION[0001]The present invention relates to the field of turbine engines and in particular to dual-flow turbine engines in which the airflows circulate from upstream downstream. It relates more specifically, but not exclusively, to an assembly of turbine engine parts comprising fan blades having an integrated platform.2. PRIOR ART[0002]Dual-flow turbine engines comprise, in a known manner, a movable fan arranged upstream of a gas generator according to the circulation of gases in the turbine engine. The gas generator is housed in an annular inner casing while the fan is housed in an annular outer casing. Said inner and outer casings are separated by an annular inter-duct casing so as to delimit a primary duct and a secondary duct. The fan comprises a plurality of fan blades and a disc, from which each blade extends substantially radially. The free ends of the blades face the outer casing so as to compress an incident air flow at least in the secondary duct and, p...

Claims

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Application Information

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IPC IPC(8): F01D11/00F01D5/22F01D5/28
CPCF01D11/008F01D5/22F01D5/282F01D5/147F05D2220/36F05D2240/80F05D2260/30F05D2300/603F01D5/146F01D11/006F04D29/083F04D29/322F04D29/324F04D29/644F04D29/667F05D2250/11F01D5/143F05D2250/23Y02T50/60
Inventor DUBOSC, MATTHIEU PIERRE MICHELBULOT, BENJAMIN
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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